An aircraft hydraulic thermal management system (10) utilizes fuel to cool hydraulic fluid (18) by means of a heat exchanger (16). A hydraulic pump (20) includes a case drain flow (25) of hydraulic fluid (18) at a first temperature T1 to drive a hydraulic motor (40); the hydraulic motor (40) circulates hydraulic fluid (18) to a reservoir (22) at a second temperature T2. The heat exchanger (16) is positioned remotely of the fuel tank (70), and has first and second channels (52, 54) positioned in thermal communication to transfer heat from the hydraulic fluid (18) to the fuel. The hydraulic motor (40) is mechanically coupled to the fuel pump (60); the hydraulic motor (40), driven by case drain flow (25) through the first channel (52), thus operates the fuel pump (60) to move fuel through the second channel (54). The thermal management system (10) is configured to assure that a) the hydraulic pump (20) circulates hydraulic fluid (18) to the reservoir (22) at the second temperature T2, and b) the second temperature T2 is always lower than the first temperature T1.
AIRCRAFT HYDRAULIC THERMAL MANAGEMENT SYSTEM
FLUGZEUGHYDRAULIK-WÄRMEREGELUNGSSYSTEM
SYSTÈME DE GESTION THERMIQUE HYDRAULIQUE D'UN AÉRONEF
2021-04-14
Patent
Electronic Resource
English
Thermal management system, aircraft and aircraft thermal management method
European Patent Office | 2023
|European Patent Office | 2022
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